Trw Limited

Other

California Institute of Technology

Northrop Grumman Systems Corporation

Tpl, Inc.

David H Lewis, Jr

Erik K Antonsson

Charles D E Lakeman

Peter D Lohn

John J Waypa

Timothy A Swann

Ernst M Faigle

Roy D Van Wynsberghe

Paul A Bowers

Homer William Fogle, Jr

Steven D Nelson

Brian R Pitstick

Douglas P Campbell

Lee D Bergerson

Ivan L Stonich

Dean M Esterberg

Christopher C Shih

Eric N Streif

Kathleen F Hodge

Wingsiu R Chan

Victor W Ruwe

David C Byers

A microelectronic battery is formed from Zn/Air technology as a volumetric energy storage device from soft lithography techniques. The microelectric battery includes an anode and a cathode disposed in an electrolyte tank having a volume &#x3c;1 mmthat is filled with an electrolyte.

Volumetric micro batteries

A pretensioner ( ) tensions vehicle seat belt webbing ( ). The pretensioner ( ) has a member ( ) movable by an actuating fluid to tension the seat belt webbing ( ). The pretensioner ( ) further has at least one microelectromechanical system (MEMS) device ( ) energizable to supply actuating fluid to move the member ( ).

Seat belt webbing pretensioner using MEMS devices

A microelectronic supercapacitor is amenable to being fabricated using micro electromechanical systems (MEMS) techniques. By utilizing MEMS techniques, the supercapacitor in accordance with the present invention can be formed with volumes <1 mm . As such, such microelectronic supercapacitor is suitable for use in applications in which only a few millimeters are available for both a supercapacitor and an energy storage device, such as a battery.

Micro-supercapacitor

A spacecraft component ( ) includes a plurality of parts, e.g., a first part ( ) and a second part ( ) connected to one another, at least the first part ( ) being mounted for movement with respect to another of the parts, e.g., the second part ( ). At least one microthruster ( ) is provided on the first part for actuation thereof and includes a chamber ( ), a fluid provided in the chamber and a diaphragm ( ) covering an opening in the chamber ( ).

Spacecraft component with microthruster actuation and operation thereof

A microthruster ( ) provides a small unit force. The microthruster is useful, for example, as a propellant for a microsatellite. The microthruster includes an aerospike ( ) extending outwardly beyond the face of an outer wall of the chamber ( ) of the microthruster in the vicinity of an outlet nozzle thereof formed by two diaphragms or burst disks ( ), closing the chamber on respective sides of the aerospike. The aerospike is preferably formed integrally with the chamber by batch microelectronic fabrication methods. Higher thrust efficiency and more controllable and uniform impulse characteristics are attainable with the microthruster and with an array ( ) comprising a plurality of the microthrusters.

Aerospike augmentation of microthruster impulse

Miniature arm fire and safe and arm devices include an electrically operated pyrotechnic initiation device ( ) to generate a detonation wave upon command and a movable pressure barrier ( ) that blocks propagation of the detonation wave if the device is not intended to be fired and opens a window ( ) to transfer the detonation wave externally of the device. The detonation wave may in alternate embodiments be a subsonic flame front and pressure wave or a supersonic shock wave, respectively. An electromagnet ( ) may serve to move the pressure barrier. Detonation waves output from the device have application in igniting an explosive train, either directly or indirectly, the latter by operating an electrical switch. In the arm fire device, the barrier automatically prevents a detonation output when electrical power is removed from the device. In the safe and arm device, the barrier, once moved out of the way, remains out of the way, even when electrical power is removed. Various forms of miniature single operate electrical switches are described that may be operated by the foregoing devices.

Mems arm fire and safe and arm devices

A pulse plasma thruster (,) utilizes a vapor producing solid (,) and a micro-sized heater (,) to produce a high pressure vapor that is directed into an ignition chamber (,) and to a thrust discharge chamber (,). The thrust discharge chamber (,) comprises two oppositely disposed electrode plates (,) and oppositely disposed fuel propellants sources (,). The passageway (,) leading from vapor producing solid (,) to the thrust discharge chamber (,) is configured to permit uniform feeding of the vapors to the thrust discharge chamber (,). A pair of electrode terminals (,) extend from the electrode plates (,) and through a housing (,). A power source (,) is coupled to the terminals (,) and provides the ignition signals necessary to cause a spark and a breakdown to a useful plasma arc by controlling the voltage-current shape of the ignition signal.

Micro pulsed plasma thruster and method of operating same

A propulsion system and, in particular, a microthruster for a microsatellite. The microthruster may be formed as a resistojet type thruster formed with a chamber, closed by a diaphragm which acts as a blow-out disk. A fluid, such as an inert gas, is disposed within the chamber. Heating of the gas causes the gas pressure to increase until the diaphragm ruptures, which, in turn, causes the gas to flow out of the chamber, acting as a propellant, and providing a small unit force. The microthruster is adapted to be formed by known batch processing methods with 10.sup.4 -10.sup.6 microthrusters per wafer. The unit of force can be easily scaled by varying the number of microthruster 20 used for an application, the geometry of the chamber 22, as well as the type of fluid used within the chamber, to suit the microsatellite application.

Integrated pulsed propulsion system for microsatellite

Growing community of inventors

Irvine, CA, United States of America

David H Lewis, Jr